EP0745530A1 - Dispositif embarqué pour la réduction de l'érosion du sol - Google Patents

Dispositif embarqué pour la réduction de l'érosion du sol Download PDF

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Publication number
EP0745530A1
EP0745530A1 EP96303903A EP96303903A EP0745530A1 EP 0745530 A1 EP0745530 A1 EP 0745530A1 EP 96303903 A EP96303903 A EP 96303903A EP 96303903 A EP96303903 A EP 96303903A EP 0745530 A1 EP0745530 A1 EP 0745530A1
Authority
EP
European Patent Office
Prior art keywords
nozzle
coolant
reducing ground
ground erosion
jet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP96303903A
Other languages
German (de)
English (en)
Other versions
EP0745530B1 (fr
Inventor
Robert George Andrew British Aero Def Ltd Angel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
Original Assignee
British Aerospace PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by British Aerospace PLC filed Critical British Aerospace PLC
Publication of EP0745530A1 publication Critical patent/EP0745530A1/fr
Application granted granted Critical
Publication of EP0745530B1 publication Critical patent/EP0745530B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/328—Application in turbines in gas turbines providing direct vertical lift
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates to means for reducing ground erosion caused by impinging hot jets, such as the jets from the propulsion and lifting gas turbine engines of Vertical/Short Take-Off and Landing (VSTOL) aircraft or the hot gases in the exhaust of vertically launched rockets.
  • VSTOL Vertical/Short Take-Off and Landing
  • apparatus for avoiding ground erosion caused by impinging hot jets such as lifting jets of VSTOL aircraft or rockets, said jets emanating from a hot jet nozzle such as a lift engine nozzle or a lift/propulsion engine nozzle, comprising means for introducing coolant fluid to an impingement surface immediately beneath the turning zone.
  • said means comprises means for directing a high pressure jet of fluid at relatively low temperature at the impingement surface, with the objective of providing an insulating film of fluid on the impingement surface, thereby reducing the heat transfer to it.
  • the fluid may be a gas such as air, or a liquid such as water, or a mixture thereof, but is preferably a fluid with a high thermal capacity, allowing a lower rate of flow to achieve a given effect.
  • the primary objective of the invention is to supply coolant fluid to the centre of jet impingement so that the fluid spreads radially over the impingement surface as uniformly as possible.
  • the fluid is arranged to flow coaxially with the impinging hot jets.
  • the coolant is introduced in a direction that does not initially correspond to the jet axis.
  • the coolant fluid is arranged to enter the jet as far downstream from the hot jet nozzle and as close to the impingement surface as possible, in order to minimise the coolant flow rate.
  • the fluid supply may be obtained from an on-board tank via a high pressure pump, and may enter the hot jet by means of a coolant nozzle fixed to, or downstream of, a lift/propulsion or lift nozzle of an engine of the aircraft.
  • the coolant nozzle may be supported and protected by a fairing. Both the coolant nozzle and fairing may be adapted or mounted so as to be able to swing into and out of the hot jet as required.
  • a downwardly-directed exhaust nozzle 1 of a gas turbine engine or fan of a VSTOL aircraft directs the gas turbine engine or fan exhaust efflux, or jet, 2 towards a ground surface 5 during vertical take-off or landing operations.
  • the jet 2 Upon impact with the ground 5 the jet 2 is diverted into a radially expanding ground jet 12.
  • the engine jet goes through a turning zone 4.
  • the engine jet is deflected laterally and radially outward from an impingement surface 6, which is directly beneath the jet 2.
  • a cusp shaped quasi stagnation region 3 is developed beneath the jet 2 as shown. Almost all ground erosion takes place on the surface encompassed by the turning zone 4, because it is here that most of the heat transfer from jet to surface takes place.
  • Figure 1b illustrates the principle of providing an insulating film of fluid to the impingement surface 6 as employed by the invention.
  • a jet of coolant such as water 7 is introduced coaxially to the engine jet flow 2 as far downstream of the engine nozzle 1 as possible. This water jet hits the impingement surface 6 and spreads outward radially as shown at 8, thus providing an insulating film of fluid on the impingement surface 6 thereby reducing the heat transfer to it.
  • Figure 2a illustrates a coolant nozzle 10 fitted to a lift engine nozzle 1.
  • the coolant nozzle 10 is coaxial with the lift engine nozzle 1 allowing a water jet 7 to flow coaxially with engine jet 2 emanating from the nozzle 1.
  • a fairing 9 supports the coolant nozzle 10 and protects it from the engine jet 2.
  • the coolant nozzle 10 is fed with water from a reservoir tank (not shown) via a pipe which passes through a side wall of the nozzle 1 and the fairing 9.
  • Figure 2b illustrates a coolant nozzle 10 fitted to a vectorable propulsion/lift engine nozzle 1.
  • the coolant nozzle 10 is again coaxial with the propulsion/lift engine nozzle 1 allowing a water jet 7 to flow coaxially with the engine jet 2 emanating from the nozzle 1.
  • a fairing 9 supports the coolant nozzle 10 and protects it from the engine jet 2.
  • the coolant nozzle 10 is fed as before from a reservoir tank (not shown).
  • Figure 2c illustrates a coolant nozzle 10 fixed downstream of a vectorable propulsion/lift engine nozzle 1.
  • the coolant nozzle 10 is coaxial with the propulsion/lift engine nozzle 1, allowing a water jet 7 to flow coaxially with engine jet 2 emanating from nozzle 1.
  • a fairing 9 supports the coolant nozzle 10 within an assembly 11 and protects it from the engine jet 2.
  • the nozzle and fairing assembly 11 is pivotally mounted to the aircraft (not shown) so that it can be swung into and out of the engine jet flow as required.
  • Figure 2d illustrates a mixed fluid coolant nozzle 10 fitted to a lift engine nozzle 1.
  • a first coolant feeder tube 13 for feeding the nozzle 10 is supported and protected by a fairing 9. Air is bled from a compressor stage of the engine (not shown) along the first coolant feeder tube 13 and a second coolant, such as water, is introduced to the coolant tube 13 at any point 14 between the compressor and the coolant nozzle 10.
  • the coolant nozzle 10 is coaxial with the lift engine nozzle 1 allowing the air/water vapour jet 7 to flow coaxially with the engine jet 2.
  • Figure 2e illustrates a mixed fluid coolant nozzle 10 fitted to a vectorable propulsion/lift engine nozzle 1.
  • a first coolant feeder tube 13 for feeding the nozzle 10 is supported and protected by a fairing 9. Air is bled from a compressor stage of the engine (not shown) along the first coolant feeder tube 13 and a second coolant, such as water, is introduced to the coolant tube 13 at any point 14 between the compressor (not shown) and the coolant nozzle 10.
  • the coolant nozzle 10 is coaxial with the propulsion/lift engine nozzle 1 allowing the air/water vapour jet 7 to flow coaxially with the engine jet 2.
  • Figure 2f illustrates a mixed fluid coolant nozzle 10 fixed downstream of a vectorable propulsion/lift engine nozzle 1.
  • the coolant nozzle 10 is coaxial with the propulsion/lift engine nozzle 1, allowing a water jet 7 to flow coaxially with engine jet 2 emanating from nozzle 1.
  • a fairing 9 supports the coolant nozzle 10 within an assembly 11 and protects it from the engine jet 2.
  • the nozzle and fairing assembly 11 is pivotally mounted to the aircraft (not shown) so that it can be swung into and out of the engine jet flow as required.
  • control of coolant fluid could be linked to signals from the aircraft's altimeter such that coolant fluid is introduced into the lifting jet(s) only as the aircraft descends through a pre-determined height above the ground and at a rate of descent that is less than the minimum permissible (for an aircraft not equipped with the invention) for a particular type of surface.
  • the coolant fluid would need to be introduced into the lifting jet at, and below, an altitude of 16.4 feet when the aircraft was descending at lees than 11.7 feet/second.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Breeding Of Plants And Reproduction By Means Of Culturing (AREA)
  • Earth Drilling (AREA)
EP96303903A 1995-06-02 1996-05-30 Dispositif embarqué pour la réduction de l'érosion du sol Expired - Lifetime EP0745530B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9511159 1995-06-02
GBGB9511159.7A GB9511159D0 (en) 1995-06-02 1995-06-02 Airbourne apparatus for ground erosion reduction

Publications (2)

Publication Number Publication Date
EP0745530A1 true EP0745530A1 (fr) 1996-12-04
EP0745530B1 EP0745530B1 (fr) 2000-07-26

Family

ID=10775392

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96303903A Expired - Lifetime EP0745530B1 (fr) 1995-06-02 1996-05-30 Dispositif embarqué pour la réduction de l'érosion du sol

Country Status (5)

Country Link
US (1) US6016996A (fr)
EP (1) EP0745530B1 (fr)
DE (1) DE69609452T2 (fr)
EA (1) EA000081B1 (fr)
GB (1) GB9511159D0 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100446333B1 (ko) * 2002-07-23 2004-09-01 주식회사 로템 액체로켓엔진의 후류가스 냉각용 인젝터
US7484589B2 (en) * 2004-03-04 2009-02-03 The Boeing Company Apparatus and method for reducing aircraft noise and acoustic fatigue
US9261047B2 (en) * 2012-05-29 2016-02-16 Lockheed Martin Corporation Jet exhaust noise reduction
JP6082415B2 (ja) * 2015-03-03 2017-02-15 富士重工業株式会社 車両の走行制御装置
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
AU2016338383A1 (en) 2015-09-02 2018-03-22 Jetoptera, Inc. Fluidic propulsive system
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
CA3068569A1 (fr) 2017-06-27 2019-01-03 Jetoptera, Inc. Configuration pour systeme de decollage et d'atterrissage vertical pour vehicules aeriens

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990905A (en) * 1957-05-13 1961-07-04 Lilley Geoffrey Michael Jet noise suppression means
FR1300094A (fr) * 1961-09-13 1962-07-27 M A N Turbomotoren G M B H Tuyère de poussée pour réacteurs
DE1756595A1 (de) * 1968-06-14 1970-08-13 Rolls Royce Gasturbinen-Hubtriebwerk
US3618701A (en) * 1969-05-22 1971-11-09 Rohr Corp Jet noise-reduction system
GB2033484A (en) * 1978-07-19 1980-05-21 Bell R Controlling aircraft engine exhaust noise
US4398667A (en) * 1976-12-23 1983-08-16 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Apparatus and method for jet noise suppression

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2359108A (en) * 1942-02-17 1944-09-26 Herbert V Hoskins Power generator
US2692024A (en) * 1950-11-25 1954-10-19 Reaction Motors Inc Jet blast cooling and quieting device
US2669091A (en) * 1951-01-13 1954-02-16 August H Schutte Gas turbine rotor cooling
AT202822B (de) * 1956-10-19 1959-04-10 Evzen Ing Mandler Verfahren und Einrichtung zum Betrieb einer Verbrennungsturbine
GB851273A (en) * 1958-04-23 1960-10-12 Power Jets Res & Dev Ltd Aircraft air intakes
GB910679A (en) * 1958-10-10 1962-11-14 Boulton Aircraft Ltd Improvements in or relating to propulsion nozzles
US3001451A (en) * 1959-01-28 1961-09-26 John A Urban Transitory exhaust deflector
DE1148820B (de) * 1960-10-06 1963-05-16 M A N Turbomotoren G M B H Hubtriebwerk fuer senkrecht startende und landende Flugzeuge
FR1318785A (fr) * 1962-01-12 1963-02-22 Bertin & Cie Perfectionnements aux trompes à jets inducteurs minces, utilisables, notamment, à la sustentation
US3226063A (en) * 1964-07-14 1965-12-28 Eleanor I Wagner Jet and rocket engine blast and sound suppressing means
GB1026068A (en) * 1964-11-09 1966-04-14 Rolls Royce Jet nozzle
GB1105817A (en) * 1965-10-22 1968-03-13 Rolls Royce Jet nozzles for jet propulsion plant
JPS59177762U (ja) * 1983-05-14 1984-11-28 鈴木　覚 タ−ボジエツトエンジンのアフタ−バ−ナ−装置

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990905A (en) * 1957-05-13 1961-07-04 Lilley Geoffrey Michael Jet noise suppression means
FR1300094A (fr) * 1961-09-13 1962-07-27 M A N Turbomotoren G M B H Tuyère de poussée pour réacteurs
DE1756595A1 (de) * 1968-06-14 1970-08-13 Rolls Royce Gasturbinen-Hubtriebwerk
US3618701A (en) * 1969-05-22 1971-11-09 Rohr Corp Jet noise-reduction system
US4398667A (en) * 1976-12-23 1983-08-16 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Apparatus and method for jet noise suppression
GB2033484A (en) * 1978-07-19 1980-05-21 Bell R Controlling aircraft engine exhaust noise

Also Published As

Publication number Publication date
GB9511159D0 (en) 1996-06-19
DE69609452D1 (de) 2000-08-31
EA199600026A3 (ru) 1997-03-31
EA000081B1 (ru) 1998-06-25
EP0745530B1 (fr) 2000-07-26
DE69609452T2 (de) 2001-01-11
US6016996A (en) 2000-01-25
EA199600026A2 (ru) 1996-12-30

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